31 Airworthiness Directives: 24 airplane, 4 engine, 1 propeller, 1 glider, 1 various.
AD 2006-20-08 · published Oct 4, 2006, effective Nov 8, 2006
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and - 145EP Airplanes
The FAA is superseding an existing airworthiness directive (AD), which applies to all EMBRAER Model EMB-145, -145ER, -145MR, - 145LR, -145XR, -145MP, and -145EP airplanes. That AD currently requires repetitive inspections to detect cracking or failure of the rod ends of the aileron power control actuator (PCA), and corrective actions if necessary. This new AD requires the same repetitive inspections of additional parts at new inspection intervals for certain airplanes; provides new corrective actions; and provides an optional terminating action for the requirements of this AD. This AD results from the issuance of mandatory continuing airworthiness information by the Brazilian airworthiness authority. We are issuing this AD to detect and correct cracking or breaking of the rod ends and connecting fittings of the aileron PCA, which could result in reduced controllability of the airplane.
AD 2006-20-11 · published Oct 4, 2006, effective Nov 8, 2006
Boeing Model 757-200, -200PF, and -200CB Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200, -200PF, and -200CB series airplanes. This AD requires doing initial and repetitive detailed or high frequency eddy current inspections for cracks around the rivets at the upper fastener row of the skin lap splice of the fuselage, and repairing any crack found. This AD results from a report indicating that certain rivets were incorrectly installed in some areas of the skin lap splices during production because they were drilled with a countersink that was too deep. We are issuing this AD to detect and correct premature fatigue cracking at certain skin lap splice locations of the fuselage, and consequent rapid decompression of the airplane.
AD 2006-20-12 · published Oct 4, 2006, effective Nov 8, 2006
McDonnell Douglas Model 717-200 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model 717-200 airplanes. This AD requires replacing the lightning critical clamp bases of the fuel tank vent system with improved clamp bases; and checking the electrical bond of the modified self-bonding mounting clamps and corrective action if necessary. This AD results from an investigation that revealed the aluminum foil strip on the nylon base of the ground clamps can fracture or separate from the base. We are issuing this AD to ensure that the fuel pipes are properly bonded to the airplane structure. Improper bonding could prevent electrical energy from a lightning strike from dissipating to the airplane structure, which could result in a fuel tank explosion.
AD 2006-20-13 · published Oct 10, 2006, effective Nov 14, 2006
Fuji Heavy Industries, Ltd. FA-200 Series Airplanes
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. We are issuing this AD to require actions that are intended to address the unsafe condition described in the MCAI.
AD 2006-21-01 · published Oct 10, 2006, effective Nov 14, 2006
Boeing Model 737 Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 737 airplanes. This AD requires repetitive measurement of the freeplay of both aileron balance tabs; repetitive lubrication of the aileron balance tab hinge bearings and rod end bearings; and related investigative and corrective actions if necessary. This AD results from reports of freeplay-induced vibration of the aileron balance tab. The potential for vibration of the control surface should be avoided because the point of transition from vibration to divergent flutter is unknown. We are issuing this AD to prevent excessive vibration of the airframe during flight, which could result in loss of control of the airplane.
AD 2006-21-02 · published Oct 10, 2006, effective Oct 25, 2006
Raytheon (Beech) Model 400, 400A, and 400T Series Airplanes; and Raytheon (Mitsubishi) Model MU-300 Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Raytheon (Beech) Model 400, 400A, and 400T series airplanes; and Raytheon (Mitsubishi) Model MU-300 airplanes. This AD requires revising the airplane flight manual to modify the Operating Limitations, Abnormal Procedures, and Normal Procedures, as applicable, for flight in icing conditions. This AD results from multiple reports of high- altitude, dual-engine flameouts on airplanes operating in certain meteorological conditions. We are issuing this AD to advise the flightcrew that the buildup of ice on certain internal areas of the engine could result in a dual-engine flameout and what action they must take to avoid this hazard.
AD 2006-20-51 · published Oct 11, 2006, effective Oct 16, 2006
Boeing Model 777-200LR Series Airplanes Powered by General Electric (GE) Model GE90-110B Engines, and Model 777-300ER Series Airplanes Powered by GE Model GE90-115B Engines
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2006-20-51 that was sent previously to all known U.S. owners and operators of certain Boeing Model 777-200LR and -300ER series airplanes by individual notices. This AD requires revising the Airplane Flight Manual to prohibit takeoffs at less than full-rated thrust. This AD is prompted by a report of two occurrences of engine thrust rollback (reduction) during takeoff. We are issuing this AD to prevent dual-engine thrust rollback, which could result in the airplane failing to lift off before reaching the end of the runway or failing to clear obstacles below the takeoff flight path.
AD 2006-21-03 · published Oct 13, 2006, effective Nov 17, 2006
Cirrus Design Corporation Models SR20 and SR22 Airplanes
The FAA adopts a new airworthiness directive (AD) for certain Cirrus Design Corporation (CDC) Models SR20 and SR22 airplanes. This AD requires you to check the maintenance records to determine whether the brake caliper piston O-ring seals were replaced at the last annual or 100-hour inspection. If the O-rings were not replaced, this AD requires you to replace the O-ring seals with new seals or replace brake calipers. This AD also requires you to modify the main landing gear wheel fairings to add temperature indicator sticker inspection holes, trim the wheel fairings to prevent them from holding fluids, install temperature indicator stickers on the brake calipers, and insert Revision A6 (with revised preflight walk-around, a limitation on the engine speed used to taxi, and brake inspection/servicing intervals) into the Pilot's Operating Handbook (POH). This AD results from several reports of airplanes experiencing brake fires and two airplanes losing directional control. We are issuing this AD to detect, correct, and prevent overheating damage to the brake caliper piston O-ring seals, which could result in leakage of brake hydraulic fluid. Consequently, this could lead to the loss of braking with loss of airplane directional control or brake fire.
AD 2006-21-04 · published Oct 13, 2006, effective Nov 17, 2006
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135BJ and EMB-145XR Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135BJ and Model EMB-145XR airplanes. This AD requires, for all airplanes, installation of an additional indication device to the clear-ice indication system. For certain airplanes, this AD requires replacing the existing clear-ice indication lamp with a new, improved lamp. For certain other airplanes, this AD also requires modifying certain electrical connections to add an indication device to the clear-ice indication system, removing a certain placard, and re- activating the clear-ice additional indicator lamp. The actions specified by this AD are intended to prevent undetected build-up of clear ice on the wing surfaces, which could lead to reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2006-21-05 · published Oct 18, 2006, effective Nov 22, 2006
Boeing Model 747-400, 777-200, and 777-300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400, 777-200, and 777-300 series airplanes. This AD requires, for certain airplanes, replacing the cell stack of the flight deck humidifier with a supplier-tested cell stack, or replacing the cell stack with a blanking plate and subsequently deactivating the flight deck humidifier. For certain other airplanes, this AD requires an inspection of the flight deck humidifier to determine certain part numbers and replacing the cell stack if necessary. This AD also allows blanking plates to be replaced with cell stacks. The actions specified by this AD are intended to prevent an increased pressure drop across the humidifier and consequent reduced airflow to the flight deck, which could result in the inability to clear any smoke that might appear in the flight deck. This action is intended to address the identified unsafe condition.
AD 2006-21-07 · published Oct 19, 2006, effective Nov 24, 2006
Airbus Model A321 Airplanes
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. We are issuing this AD to require actions to correct the unsafe condition on these products.
AD 2006-21-08 · published Oct 19, 2006, effective Nov 3, 2006
Airbus Model A330-200, A340-200, and A340-300 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, A340-200, and A340-300 airplanes. This AD requires the installation of heatshields in the belly fairing of the center fuselage. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent exposing any fuel leaked from the center fuel tank to the hot temperature areas of the air conditioning packs, which could result in a fire and consequent fuel tank explosion.
AD 2006-21-09 · published Oct 19, 2006, effective Nov 3, 2006
Boeing Model 777-200 Series Airplanes Equipped with General Electric GE90-94B Engines
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200 series airplanes equipped with General Electric GE90-94B engines. This AD requires inspecting to determine the part number of the identification plate of the torque box on the thrust reversers (TRs), and investigative and corrective actions if necessary. This AD results from engine certification testing which revealed that TRs on GE90-94B engines have inner walls that could develop disbonding in the upper bifurcation radii. Disbonding was found in an equivalent inner wall used during the testing. We are issuing this AD to prevent failure of a TR and adjacent components and their consequent separation from the airplane during flight or during a refused takeoff (RTO). These separated components could cause structural damage to the airplane or damage to other airplanes and possible injury to people on the ground. TR failure during a RTO could also cause the engine to produce forward thrust, resulting in asymmetric thrust and possible runway excursion.
AD 2006-21-12 · published Oct 19, 2006, effective Nov 8, 2006
AeroSpace Technologies of Australia Pty Ltd. Models N22B, N22S, and N24A Airplanes
The FAA is adopting a new airworthiness directive (AD) to supersede AD 2003-22-13, which applies to all AeroSpace Technologies of Australia Pty Ltd. (ASTA) Models N22B and N24A airplanes. AD 2003-22-13 currently requires you to visually inspect the ailerons for damage and replace if necessary; adjust the engine power levers aural warning microswitches; set flap extension and flap down operation limitations; and fabricate and install cockpit flap extension and flap down operation restriction placards. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Australia. The FAA inadvertently omitted Model N22S airplanes from the applicability of AD 2003-22-13. Therefore, this AD retains the actions exactly as required in AD 2003-22-13 and adds Model N22S airplanes to the Applicability section. We are issuing this AD to prevent failure of the aileron due to undetected pre-existing aileron damage and airplane operation outside of the approved limits. Aileron failure could lead to reduced or loss of control of the airplane.
AD 2006-21-06 · published Oct 25, 2006, effective Nov 29, 2006
McDonnell Douglas Model DC-9-10 Series Airplanes; DC-9-20 Series Airplanes; DC-9-30 Series Airplanes; DC-9-40 Series Airplanes; and DC-9-50 Series Airplanes
The FAA is superseding an existing airworthiness directive (AD), which applies to certain McDonnell Douglas transport category airplanes. That AD currently requires, among other things, revision of an existing program of structural inspections. This new AD requires implementation of a program of structural inspections of baseline structure to detect and correct fatigue cracking in order to ensure the continued airworthiness of these airplanes as they approach the manufacturer's original fatigue design life goal. This AD results from a significant number of these airplanes approaching or exceeding the design service goal on which the initial type certification approval was predicated. We are issuing this AD to detect and correct fatigue cracking that could compromise the structural integrity of these airplanes.
AD 2006-22-01 · published Oct 27, 2006, effective Dec 1, 2006
Boeing Model 757-200, -200CB, and -300 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200, -200CB, and -300 series airplanes. This AD requires repetitive detailed inspections for proper functioning of the girt bar leaf springs for the escape slides to ensure the leaf springs retain the sliders and the required 0.37-inch minimum engagement between the sliders and floor fittings is achieved at passenger doors 1, 2, and 4, and corrective actions if necessary. This AD results from a report that the escape slides failed to deploy correctly during an operator's tests of the escape slides. We are issuing this AD to prevent escape slides from disengaging from the airplane during deployment or in use, which could result in injuries to passengers or flightcrew.
AD 2006-22-02 · published Oct 27, 2006, effective Dec 1, 2006
Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300-600 series airplanes. That AD currently requires an inspection for evidence of chafing between the hydraulic flexible hose and the ram air turbine (RAT) hub, and related investigative and corrective actions if necessary. This new AD extends the applicability to include all Model A300-600 series airplanes that are equipped with a certain RAT. This AD results from reports of holes in the RAT hub cover. We are issuing this AD to prevent a hole in the RAT hub cover. A hole in the RAT hub cover could allow water to enter the RAT governing mechanism, freeze during flight, and jam the governing mechanism. In addition, the metal particles that result from chafing between the hydraulic flexible hose and the RAT could mix with the lubricant grease and degrade the governing mechanism. In an emergency, a jammed or degraded RAT could result in its failure to deploy, loss of hydraulic pressure or electrical power to the airplane, and consequent reduced controllability of the airplane.
AD 2006-22-03 · published Oct 27, 2006, effective Dec 1, 2006
Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Model A310 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus models, as specified above. This AD requires modifying the aft pressure bulkhead for improved corrosion protection and drainage, and related concurrent actions. This AD results from severe corrosion found in the lower rim area of the aft pressure bulkhead during routine maintenance of an airplane. We are issuing this AD to prevent corrosion on the inner rim angle and cleat profile splice of the aft pressure bulkhead, which could result in the loss of airplane structural integrity.
AD 2006-22-07 · published Oct 27, 2006, effective Dec 1, 2006
Airbus Model A300 and A310 Airplanes; and Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)
The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A300 and A310 airplanes and A300-600 series airplanes. This AD requires inspecting for discrepancies of all electrical bundles located in the leading and trailing edges of the wings, and performing corrective actions if necessary. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent an ignition source, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
AD 2006-22-08 · published Oct 27, 2006, effective Dec 1, 2006
Air Tractor, Inc. Models AT-602, AT-802, and AT-802A Airplanes
The FAA adopts a new airworthiness directive (AD) for all Air Tractor, Inc. Models AT-602, AT-802, and AT-802A airplanes. This AD requires you to repetitively inspect the engine mount for any cracks, repair or replace any cracked engine mount, and report any cracks found to the FAA. This AD results from reports of cracked engine mounts. We are issuing this AD to detect and correct cracks in the engine mount, which could result in failure of the engine mount. Such failure could lead to separation of the engine from the airplane.
AD 2006-22-09 · published Oct 27, 2006, effective Dec 1, 2006
Boeing Model 747 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747 airplanes. This AD requires repetitive mid- and low-frequency eddy current inspections for cracks in the overlapped skin panels in the fuselage skin lap joints in sections 41, 42, 44, and 46, and corrective actions if necessary. This AD results from a report indicating that an operator found multiple small cracks in the overlapped skin panels in the fuselage skin lap joints. We are issuing this AD to detect and correct cracks in the overlapped skin panels, which could join together and result in reduced structural capability in the skin and consequent rapid decompression of the airplane.
AD 2006-22-11 · published Oct 27, 2006, effective Dec 1, 2006
EADS SOCATA Model TBM 700 Airplanes
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as unsatisfactory initial elevator trim actuator greasing, which may lead to the icing of the elevator trim and generate an untrimmed nose-up attitude after an autopilot disconnection. We are issuing this AD to require actions to correct the unsafe condition on these products.
AD 2006-22-04 · published Oct 30, 2006, effective Dec 4, 2006
Airbus Model A318-100 and A319-100 Series Airplanes; Model A320-111 Airplanes; Model A320-200, A321-200, A330-200, A330-300, A340-200, and A340-300 Series Airplanes; Model A340-541 Airplanes; and Model A340-642 Airplanes; Equipped With Certain Sogerma-Services Powered Seats
The FAA is adopting a new airworthiness directive (AD) for certain Airbus airplane models identified above. This AD requires inspecting to determine if a certain actuator is installed in the pilot's or co-pilot's seat, and doing applicable corrective actions. For certain actuators, the AD also requires replacing rotors on both vertical and horizontal movements with new rotors, and replacing the clutch cap with a new cap. This AD results from a report of heavy wear at the driving gear of the rotor shaft end of the electrical driven motor on certain actuators of the pilot's and co-pilot's seats. We are issuing this AD to prevent uncommanded movement of the pilot's or co- pilot's seat during takeoff or landing, which could result in interference with the operation of the airplane and consequent temporary loss of airplane control.
AD 2006-22-06 · published Oct 30, 2006, effective Nov 14, 2006
Bombardier Inc. Airplanes
The FAA is superseding an existing airworthiness directive (AD) that applies to certain Bombardier Model CL-600-2B16 (CL-604) airplanes and Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. These models may be referred to by their marketing designations as RJ100, RJ200, RJ440, CRJ100, CRJ200, CRJ440, and CL-65. The existing AD currently requires revising the Emergency Procedures section of the airplane flight manual (AFM) to advise the flightcrew of additional procedures to follow in the event of stabilizer trim runaway. For certain airplanes, the existing AD also requires revising the Abnormal Procedures section of the AFM to advise the flightcrew of procedures to follow in the event of MACH TRIM, STAB TRIM, and horizontal stabilizer trim malfunctions. This AD requires revising the same Emergency and Abnormal Procedures sections of the AFM to advise the flightcrew of revised/additional procedures. This AD also requires revising the Normal section of the AFM to require a review of the location of certain circuit breakers and a functional check of the stabilizer trim system. This AD also requires installing circuit breaker identification collars and provides an optional terminating action for the requirements of the AD. This AD also removes airplanes from the applicability of the existing AD. This AD results from reports of uncommanded horizontal stabilizer trim motion. We are issuing this AD to ensure that the flightcrew is advised of appropriate procedures to follow in the event of uncommanded movement or stabilizer trim runaway. Failure to follow these procedures could result in excessive uncommanded movement of the horizontal stabilizer trim actuator (HSTA) and loss of ability to use trim switches to override uncommanded movement or yoke disconnect switches to disconnect the HSTA, which could result in reduction of or loss of pitch control and consequent reduced controllability of the airplane. \n\n\nDATES: This AD becomes effective November 14, 2006. \n\n\tThe Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of November 14, 2006. \n\n\tOn September 1, 2006 (71 FR 51990, September 1, 2006), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD. \n\n\tWe must receive any comments on this AD by December 29, 2006.
AD 97-06-13 R1 · published Oct 2, 2006, effective Oct 2, 2006
Rolls-Royce plc Engines
This amendment rescinds airworthiness directive (AD) 97-06-13 for Rolls-Royce plc (RR) models RB211 Trent 892, 884, 877, 875, and 892B series turbofan engines. That AD requires inspecting and replacing certain angle gearbox and intermediate gearbox hardware, and on-going repetitive inspections of the magnetic chip detectors. That AD resulted from reports of loss of oil from the angle drive upper shroud tube, the intermediate gearbox housing, the external gearbox lower bevel box housing, and by reports of bearing failures. We intended the requirements of that AD to prevent loss of oil, which could cause an engine fire, and to prevent in-flight engine shutdowns and airplane diversions caused by oil loss and from bearing failures. Since we issued that AD, we determined that the inspections and replacements required by that AD are no longer required to correct an unsafe condition.
AD 2006-17-07 R1 · published Oct 18, 2006, effective Nov 2, 2006
Pratt & Whitney Division Engines
The FAA is revising an existing airworthiness directive (AD) for Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, and -219 turbofan engines. That AD currently requires either replacing high pressure compressor (HPC) front hubs and HPC disks that have operated at any time with PWA 110-21 coating and that operated in certain engine models, or, visually inspecting and fluorescent penetrant inspecting (FMPI) for cracking of those parts and re-plating them if they pass inspection. This AD requires the same actions, but makes necessary corrections to inadvertent reference errors and omissions found in AD 2006-17-07, and relaxes some of the compliance times in Table 5. This AD results from our finding reference errors and omissions in AD 2006- 17-07, from determining that the AD as drafted imposed an unnecessary burden on operators if they have to immediately remove engines, and from requests to clarify compliance paragraphs. We are issuing this AD to prevent a rupture of an HPC front hub or an HPC disk that could result in an uncontained engine failure and damage to the airplane. \n\nDATES: This AD becomes effective November 2, 2006. The Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulations as of October 4, 2006 (71 FR 51459, August 30, 2006).
AD 2006-21-10 · published Oct 19, 2006, effective Nov 24, 2006
Turbomeca Arriel 2B Series Turboshaft Engines
The FAA is adopting a new airworthiness directive (AD) for Turbomeca Arriel 2B, 2B1, and 2B1A turboshaft engines. This AD requires visually inspecting the splines of the high-pressure (HP) pump drive gear shaft and coupling shaft assembly for wear. This AD results from reports of uncommanded in-flight shutdowns of engines. We are issuing this AD to detect wear on the splines of the HP pump drive gear shaft and coupling shaft assembly, which could interrupt the fuel flow and cause an uncommanded in-flight shutdown of the engine on a single- engine helicopter. The in-flight shutdown of the engine could result in a forced autorotation landing or accident.
AD 2006-21-11 · published Oct 19, 2006, effective Nov 3, 2006
Turbomeca Turmo IV A and IV C Series Turboshaft Engines
The FAA is adopting a new airworthiness directive (AD) for Turbomeca Turmo IV A and IV C series turboshaft engines. This AD requires identifying, inspecting and replacing flexible lubrication pipes manufactured after April 1, 2003. If both engines on the same helicopter each have an affected pipe, then this AD requires replacing one of the affected pipes before further flight. This AD also requires initial and repetitive borescope inspections of affected pipes, visual inspections for oil leakage, and visual inspections of the oil filter, on engines that are not required to have an affected pipe replaced before further flight by this AD. This AD results from 7 reports of oil leakage due to the deterioration of flexible lubrication pipes manufactured after April 1, 2003. We are issuing this AD to prevent dual-engine failure on a twin-engine helicopter.
AD 2006-22-12 · published Oct 27, 2006, effective Nov 13, 2006
Hartzell Propeller Inc. Model HC-B5MP-3( )/M10282A( )+6 and HC-B5MP-3( )/M10876( )( )( )( ) Five-Bladed Propellers.
The FAA is superseding an existing airworthiness directive (AD) for Hartzell Propeller Inc. model HC-B5MP-3( )/M10282A( )+6 five- bladed propellers. That AD currently requires initial and repetitive torque check inspections on the mounting bolts on certain model Hartzell Propeller Inc. HC-B5MP-3( )/M10282A( )+6 five-bladed propellers, replacement of mounting bolts if necessary, and inspection and resurfacing of the engine and propeller mounting flanges if necessary. This AD requires the same actions but requires more detailed overhaul inspections and maintenance than the previous AD, AD 2004-21- 01. This AD also adds Hartzell Propeller Inc. HC-B5MP-3( )/M10876( )( )( )( ) five-bladed propellers to the applicability. This AD results from reports of fretting wear still occurring between the engine and propeller mounting flanges. The fretting wear results in loss of mounting bolt preload, causing failure of the mounting bolts. We are issuing this AD to prevent propeller separation from the airplane.
AD 2006-22-10 · published Oct 27, 2006, effective Dec 1, 2006
Schempp-Hirth GmbH & Co. KG Models Mini-Nimbus B and Mini-Nimbus HS-7 Sailplanes
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a failure in the flap actuating circuit. An investigation showed that the lever at the torsional drive in the fuselage failed at the weld. We are issuing this AD to require actions to correct the unsafe condition on these products.
AD 2006-22-05 · published Oct 27, 2006, effective Dec 1, 2006
Various Aircraft Equipped With Honeywell Primus II RNZ-850( )/-851( ) Integrated Navigation Units
The FAA is superseding an existing airworthiness directive (AD), which applies to various aircraft equipped with certain Honeywell Primus II RNZ-850( )/-851( ) integrated navigation units (INUs). That AD, as one alternative for compliance, provides for a one-time inspection to determine whether a certain modification has been installed on the Honeywell Primus II NV-850 navigation receiver module (NRM), which is part of the INU. In lieu of accomplishing this inspection, and for aircraft found to have an affected NRM, the existing AD provides for revising the aircraft flight manual to include new limitations for instrument landing system approaches. This new AD requires inspecting to determine whether certain modifications have been done on the NRM; and doing related investigative, corrective, and other specified actions, as applicable; as well as further modifications to address additional anomalies. This AD results from reports indicating that erroneous glideslope indications have occurred on certain aircraft equipped with the subject INUs. We are issuing this AD to ensure that the flightcrew has an accurate glideslope deviation indication. An erroneous glideslope deviation indication could lead to the aircraft making an approach off the glideslope, which could result in impact with an obstacle or terrain.
